1. Team 3 Structures and Weights PDR 2
Presented by:
Stacie Pedersen
Jason Hargraves
Lazo Trkulja

2. Overview Landing Gear Weights Model Wing Structure Wing Load Analysis
Fuselage and Tail Structure

3. Landing Gear Analysis Layout according to Raymer
Lateral tip-over at 30°
Longitudinal tip-over at 15°
19.4 in
9.6 in
b/2=27.8 in.
46.8 in

4. Landing Gear Layout b=55.6 in L=46.8 in Wingtip strike at 17° bank
Tail strike negligible ---exceeds 15° tip-over
Approx. 1.5 in propeller ground clearance CG

5. Weights Model Current Take-off Weight  1.92 lbs
Airframe Weight Breakdown
Wing  0.54 lbs
Canard  0.09 lbs
Vertical Stabilizer lbs
Fuselage  0.22 lbs

6. Weights Cont. CG
Moments of inertia

7. Summary Weights Breakdown
Weight (lbs.)
Arm
(ft.)
Moment
(ft.-lbs.)
Airframe
0.92
-0.17
-0.15
Propulsion
0.55
-2.14
-1.18
Avionics
0.28
-0.32
-0.09
Landing Gear
0.11
-1.13
-0.12
Miscellaneous
0.06
-0.63
-0.04
TOTAL
1.92
-0.85
-1.64
Origin at wing root c/4
Nose-up moments are positive

8. Airframe Weights Weight (lbs.) Arm (ft.) Moment (ft.-lbs.) Wing 0.53
0.24
0.13
Canard
0.10
-1.80
-0.19
Vertical Stabilizer
0.06
0.54
0.03
Fuselage
0.22
-0.58
-0.13
AIRFRAME
0.92
-0.17
-0.15

9. Propulsion Weights Weight (lbs.) Arm (ft.) Moment (ft.-lbs.) Battery
0.086
-1.17
-0.10
ESC
0.026
-1.42
-0.04
Motor
0.163
-2.21
-0.36
Gearbox
0.156
-2.43
-0.38
Propeller
0.120
-2.53
-0.30
PROPULSION
0.551
-2.14
-1.18

10. Avionics Weights Weight (lbs.) Arm (ft.) Moment (ft.-lbs.) Receiver
0.094
-0.84
-0.08
Gyro
0.031
-0.92
-0.03
Ruder Servo
0.020
0.35
0.01
Elevator Servo
-1.94
Flaperon Servos
0.040
0.00
Gear Servo
0.077
AVIONICS
0.282
-0.32
-0.09

11. Landing Gear Weights Weight (lbs.) Arm (ft.) Moment (ft.-lbs.)
Main Gear
0.056
-0.73
-0.04
Main Wheels
0.004
0.00
Nose Gear
0.044
-1.82
-0.08
Nose Wheel
0.002
LANDING GEAR
0.106
-1.13
-0.12

12. Wing Structure Balsa Skin (wing covering) Blue Foam
Leading Edge Balsa Spar
Balsa Control Surface
Attachment Spar
Balsa Skin (wing covering)
Blue Foam

13. Wing Root Structural Dimensions
0.97 ft
0.194 ft
0.04 ft
Trailing Edge Spar Thickness  3/16 in Balsa

14. Wing Structure

15. Wing Load Distribution
Assume Elliptical Loading: e=1
USNPS-4

16. Bending Equations
To find max allowable tensile & compressive bending moments
Modeled as beam with no taper
To find moments and deflections

17. Bending Results

18. Bending Results Max Allowable Tensile Moment  31.83 lbf-ft
Max Allowable Compressive Moment
 lbf-ft
Max Bending Moment in Loiter
 9.18 lbf-ft
Max Bending Moment in Turning Flight
9.73 lbf-ft

19. V-n Diagram

20. Torsion Equations and Assumptions
Torque Resultant
Chord Equation
T = ft-lbs.

21. Failure, Deflection and Inertias
Failure occurs at 2.25 Gs
Excludes reinforcement from fillets
Will demonstrate 2.0 Gs prior to flight
Max tip deflection  0.04 ft
Ixx = 2.50 lb-ft2
Iyy = 1.08 lb-ft2
Izz = 1.74 lb-ft2

22. Fuselage Structure
Foam Panels
Hollow
Inner Balsa Box

23. Wing & Canard Attachment to Fuselage
Wing will attach to the bottom of the fuselage via a foam saddle piece between the wing and the inner fuselage box
Canard will attach to the fuselage similar to the wing

24. Vertical Tail Construction
0.80 ft
0.30 ft
0.76 ft
Vertical tail will attach to the fuselage using tri-stock on each side of base

25. Questions